Aerospace Science and Technology最新文献

英文中文

On flight instabilities of capsule-rigid parachute system during supersonic planetary descent

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-06 DOI: 10.1016/j.ast.2025.110026

Luca Placco , Giulio Soldati , Matteo Bernardini , Francesco Picano

High-fidelity time-evolving simulations of a rigid parachute trailing behind a descent module in a supersonic flight regime have been performed, employing Large-Eddy Simulation (LES) and Immersed-Boundary Method (IBM) techniques. The study aims to establish the fluid dynamic nature of the ‘breathing’ instability present also in a rigid decelerator, and thus its independence from structural flexibility. The turbulent wake of the descent capsule interacts with the bow shock generated by the parachute acting as the primary triggering factor. Energetic turbulent structures, accurately resolved by Large-Eddy Simulation, induce local fluctuations in the parachute shock, destabilizing its equilibrium with the upstream flow and leading to continuous cyclic motion of the shock wave. This motion correlates with periodic variations in flow pressure inside the canopy control volume, impacting parachute performance. Based on simulation results, a zero-dimensional model is developed to predict the unsteady dynamics of the shock motion and the decelerator performance. The model is driven by input fluctuations from the capsule wake, reproducing the main frequencies of shock position oscillations and drag variations as observed in simulations. It is apparent that unsteadiness is eventually triggered by low-frequency wake perturbations. Thus, the study provides insights into factors contributing to unsteady parachute responses in supersonic regimes.

{"title":"On flight instabilities of capsule-rigid parachute system during supersonic planetary descent","authors":"Luca Placco , Giulio Soldati , Matteo Bernardini , Francesco Picano","doi":"10.1016/j.ast.2025.110026","DOIUrl":"10.1016/j.ast.2025.110026","url":null,"abstract":"<div><div>High-fidelity time-evolving simulations of a rigid parachute trailing behind a descent module in a supersonic flight regime have been performed, employing Large-Eddy Simulation (LES) and Immersed-Boundary Method (IBM) techniques. The study aims to establish the fluid dynamic nature of the ‘breathing’ instability present also in a rigid decelerator, and thus its independence from structural flexibility. The turbulent wake of the descent capsule interacts with the bow shock generated by the parachute acting as the primary triggering factor. Energetic turbulent structures, accurately resolved by Large-Eddy Simulation, induce local fluctuations in the parachute shock, destabilizing its equilibrium with the upstream flow and leading to continuous cyclic motion of the shock wave. This motion correlates with periodic variations in flow pressure inside the canopy control volume, impacting parachute performance. Based on simulation results, a zero-dimensional model is developed to predict the unsteady dynamics of the shock motion and the decelerator performance. The model is driven by input fluctuations from the capsule wake, reproducing the main frequencies of shock position oscillations and drag variations as observed in simulations. It is apparent that unsteadiness is eventually triggered by low-frequency wake perturbations. Thus, the study provides insights into factors contributing to unsteady parachute responses in supersonic regimes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110026"},"PeriodicalIF":5.0,"publicationDate":"2025-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143387894","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Handling Qualities sizing for aerial vehicles based on control moment polytopes

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-05 DOI: 10.1016/j.ast.2025.110020

Aristeidis Antonakis

The study of Handling Qualities (HQ) constitutes an integral part of the air vehicle design process, ensuring safety and flyability. Nevertheless, traditional HQ sizing methods derived for conventional aircraft configurations provide decreasing insight on modern, unconventional, flight-control-augmented vehicles, mainly due to the lack of related operational experience. In this article, a new HQ sizing methodology is proposed aiming at a more vehicle-agnostic approach than existent techniques. Based on the concept of state-space polytopes, the method provides a means for visualizing the HQ requirements and comparing them to the vehicle's control authority. The polytopic representation serves to compact the dynamic HQ requirements down to a limited number of quasi-equilibrium calculations and allows for the analytic derivation of “HQ gradients” with respect to the vehicle's design features; simultaneously, non-linear control saturation aspects are accounted for. Test cases on two vehicles with complex, yet very different HQ characteristics - a Blended-Wing-Body (BWB) aircraft and an electric Vertical Take Off and Landing (eVTOL) vehicle - are selected to demonstrate the technique's effectiveness and potential application domain.

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引用次数: 0

Suppression of flow separation of a high-lift wing with active flow control

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-05 DOI: 10.1016/j.ast.2025.110017

Qiangqiang Sun , Faycal Bahri , Mark Jabbal , Wit Stryczniewicz , Richard Jefferson-Loveday , Bruno Stefes , Alexander Büscher

Flow separation caused by the integration of a leading edge slat cut-out to accommodate an ultra-high bypass ratio engine reduces the maximum lift coefficient. In this study, an active flow control approach including 88 pulsed jet nozzles near the leading edge is used to control flow separation over a multi-element high-lift aerofoil. A hybrid large-eddy simulation (LES) and stress-blended eddy simulation (SBES) method is deployed to analyze flow physics and wind tunnel tests are also performed for the flow with/without control. The results show that severe flow separation is observed for the clean case by visualizing the streamlines on the airfoil's surface via numerical and experimental methods. Compared with the clean case, the stall angle is delayed by around 4°, and the maximum lift coefficient is increased by more than 15% after deploying the active flow control. Meanwhile, when the active flow control is imposed, a lift enhancement region caused by the vortex shedding downstream of the jet nozzles is formed adjacent to the leading edge, and its scale becomes larger along the spanwise direction.

{"title":"Suppression of flow separation of a high-lift wing with active flow control","authors":"Qiangqiang Sun , Faycal Bahri , Mark Jabbal , Wit Stryczniewicz , Richard Jefferson-Loveday , Bruno Stefes , Alexander Büscher","doi":"10.1016/j.ast.2025.110017","DOIUrl":"10.1016/j.ast.2025.110017","url":null,"abstract":"<div><div>Flow separation caused by the integration of a leading edge slat cut-out to accommodate an ultra-high bypass ratio engine reduces the maximum lift coefficient. In this study, an active flow control approach including 88 pulsed jet nozzles near the leading edge is used to control flow separation over a multi-element high-lift aerofoil. A hybrid large-eddy simulation (LES) and stress-blended eddy simulation (SBES) method is deployed to analyze flow physics and wind tunnel tests are also performed for the flow with/without control. The results show that severe flow separation is observed for the clean case by visualizing the streamlines on the airfoil's surface via numerical and experimental methods. Compared with the clean case, the stall angle is delayed by around 4°, and the maximum lift coefficient is increased by more than 15% after deploying the active flow control. Meanwhile, when the active flow control is imposed, a lift enhancement region caused by the vortex shedding downstream of the jet nozzles is formed adjacent to the leading edge, and its scale becomes larger along the spanwise direction.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110017"},"PeriodicalIF":5.0,"publicationDate":"2025-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143349065","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental and numerical research on combined design of corner separation in compressor

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-05 DOI: 10.1016/j.ast.2025.110029

Tongtong Meng , Xin Li , Xinyu Ren , Ling Zhou , Lucheng Ji

In this manuscript, to simultaneously inhibit multiple causes of corner separation and therefore improve the flow around endwall as much as possible, the combined control by both Full Blended Blade and Endwall (Full-BBEW) and endwall Vortex Generator (VG) are studied. Firstly, a Full-BBEW design is built for a linear cascade and then an combined control is carefully designed by placing a VG in the middle passage of Full-BBEW design. Both numerical and experimental analyses over the entire working condition are performed. Results demonstrate that the combined design significantly reduces overall aerodynamic losses across the full range of design Mach number, with a more pronounced effect observed at high incidence angles. The combined BBEW and VG design provides a comprehensive control strategy that mitigates corner separation and improves endwall flow, resulting in improved aerodynamic performance.

引用次数: 0

Structural topology optimization of aircraft wing leading edge fabricated of multilayer composites

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-04 DOI: 10.1016/j.ast.2025.109993

Yihao Dong , Irfan Hussain , Shaoming He

Slat is a lift-improvement device at the leading edge of the aircraft construction. This component should be rigid enough under aerodynamic loads, and impact-resistant after a strike from birds or other foreign objects. This work presents a Topology Optimization (TO) strategy in the design of aircraft slat structure, which takes both aerodynamic bearing capacity and multilayer composites into consideration. The proposed structure has two typical characteristics: the topologically optimized cross-section and the layout is functionally gradient. The optimized slat structure is filled with aluminum foam and wrapped by sandwich coatings (laminated by an aluminum honeycomb layer and composite faceplate). Three different layers' arrangements are interpolated and topologically optimized by the approach for comparison. Boundary conditions have considered dynamic shape, de-ice tube and two typical aerodynamic loading cases. The obtained structures are then simulated through the Smooth Particle Hydrodynamics (SPH) bird striking test. Compared to the original metallic slat structure, the TO slat with sandwich shell significantly improves stiffness under aerodynamic load, reduces 28.9% structural weight, absorbs an additional 24.1% of striking energy, and reduces the damaged area by 1.28% in a typical bird striking event on a 2.88 m length slat structure. The proposed layout can be fabricated by matched moulding.

{"title":"Structural topology optimization of aircraft wing leading edge fabricated of multilayer composites","authors":"Yihao Dong , Irfan Hussain , Shaoming He","doi":"10.1016/j.ast.2025.109993","DOIUrl":"10.1016/j.ast.2025.109993","url":null,"abstract":"<div><div>Slat is a lift-improvement device at the leading edge of the aircraft construction. This component should be rigid enough under aerodynamic loads, and impact-resistant after a strike from birds or other foreign objects. This work presents a Topology Optimization (TO) strategy in the design of aircraft slat structure, which takes both aerodynamic bearing capacity and multilayer composites into consideration. The proposed structure has two typical characteristics: the topologically optimized cross-section and the layout is functionally gradient. The optimized slat structure is filled with aluminum foam and wrapped by sandwich coatings (laminated by an aluminum honeycomb layer and composite faceplate). Three different layers' arrangements are interpolated and topologically optimized by the approach for comparison. Boundary conditions have considered dynamic shape, de-ice tube and two typical aerodynamic loading cases. The obtained structures are then simulated through the Smooth Particle Hydrodynamics (SPH) bird striking test. Compared to the original metallic slat structure, the TO slat with sandwich shell significantly improves stiffness under aerodynamic load, reduces 28.9% structural weight, absorbs an additional 24.1% of striking energy, and reduces the damaged area by 1.28% in a typical bird striking event on a 2.88 m length slat structure. The proposed layout can be fabricated by matched moulding.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 109993"},"PeriodicalIF":5.0,"publicationDate":"2025-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143377176","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Explicit solution for the attitude motion of a bias momentum satellite under Bdot magnetic damping

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-04 DOI: 10.1016/j.ast.2025.110019

D.S. Roldugin, M.Yu. Ovchinnikov

A bias momentum satellite motion in the stabilization phase is considered. The satellite is equipped with a pitch momentum wheel that maintains a constant rotation rate, and three-axis magnetorquers set. The wheel axis should point along the orbital normal which is the stable position, thus enabling roll/yaw passive stability, without active pitch stabilization. To achieve convergence to this attitude, active attitude damping with Bdot control is employed, which ensures asymptotic stability. An explicit form of approximate solution of the equations of motion is obtained for a polar satellite. Through a comparison between Bdot and asymptotic damping algorithms, the superior performance of Bdot control in this specific scenario is demonstrated.

引用次数: 0

Fixed-time attitude control of flying-wing unmanned aerial vehicles based on plasma control surface

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-04 DOI: 10.1016/j.ast.2025.110016

Zhouhang Wei , Jingping Shi , Yeguang Wang , Yongxi Lyu , Yunhao Fu , Xiaoguang Wang

This paper investigates rudderless control in flying-wing unmanned aerial vehicles (UAVs) equipped with a plasma Gurney flap. To solve this problem, we propose a dynamic surface fixed-time controller based on a finite-time extended state observer. The distribution of dielectric barrier discharge plasma actuators and their application strategy for a small flying-wing UAV are derived. The aerodynamic data of the plasma control surface are calculated using the computational fluid dynamics software FLUENT, allowing a comprehensive analysis to be carried out. A fixed-time backstepping control method for the dynamic surface based on a finite-time extended state observer is proposed. The finite-time extended state observer is designed to suppress the influence of external disturbances and model uncertainties on the UAV's attitude, and the fixed-time filter effectively eliminates the explosion of complexity encountered in backstepping control strategies. A continuously differentiable strict Lyapunov stability function proves that the proposed controller guarantees the fixed-time stability of the system. Simulation results show that the proposed control method can realize small-angle attitude control of a UAV without using a mechanical control surface and has strong anti-disturbance and attitude tracking capabilities.

{"title":"Fixed-time attitude control of flying-wing unmanned aerial vehicles based on plasma control surface","authors":"Zhouhang Wei , Jingping Shi , Yeguang Wang , Yongxi Lyu , Yunhao Fu , Xiaoguang Wang","doi":"10.1016/j.ast.2025.110016","DOIUrl":"10.1016/j.ast.2025.110016","url":null,"abstract":"<div><div>This paper investigates rudderless control in flying-wing unmanned aerial vehicles (UAVs) equipped with a plasma Gurney flap. To solve this problem, we propose a dynamic surface fixed-time controller based on a finite-time extended state observer. The distribution of dielectric barrier discharge plasma actuators and their application strategy for a small flying-wing UAV are derived. The aerodynamic data of the plasma control surface are calculated using the computational fluid dynamics software FLUENT, allowing a comprehensive analysis to be carried out. A fixed-time backstepping control method for the dynamic surface based on a finite-time extended state observer is proposed. The finite-time extended state observer is designed to suppress the influence of external disturbances and model uncertainties on the UAV's attitude, and the fixed-time filter effectively eliminates the explosion of complexity encountered in backstepping control strategies. A continuously differentiable strict Lyapunov stability function proves that the proposed controller guarantees the fixed-time stability of the system. Simulation results show that the proposed control method can realize small-angle attitude control of a UAV without using a mechanical control surface and has strong anti-disturbance and attitude tracking capabilities.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110016"},"PeriodicalIF":5.0,"publicationDate":"2025-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143377178","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Predicting high-cycle fatigue strength and three-dimensional fatigue crack growth in simulated compressor blade by phase-field model

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-04 DOI: 10.1016/j.ast.2025.110009

Shen Sun , Shijie Liu , Weiwei He , Xuan Zhang , Wei Tang , Liucheng Zhou , Min Yi

High-cycle fatigue is a major concern for aeroengine compressor blades under complex cyclic mechanical and aerodynamic loads, but predicting fatigue behavior of blades remains challenging. Herein, a phase-field fatigue fracture model is applied to simulate the high-cycle fatigue behavior of the simulated compressor blade. In the phase-field model, a logarithmic degradation function is adopted to describe the fracture toughness decreasing with fatigue cycles. Cyclic loads are mimicked by the pressure applied on the blade surface. The three-dimensional (3D) fatigue crack propagation of the simulated blade is simulated. It is found that the fatigue crack initiates at the variable cross-section and propagates horizontally. Laser shock peening (LSP) is further shown to improve the fatigue properties, i.e., LSP induced compressive residual stress results in a 95% increase of fatigue life and notably retards the 3D fatigue crack growth. For the fatigue strength of both the original and LSPed blades, the predictions are within the

\pm 5 %

error band. The phase-field model here provides a predictive approach for the evaluation of high-cycle fatigue behavior and shows a great potential in the optimal design of durable and reliable compressor blades.

{"title":"Predicting high-cycle fatigue strength and three-dimensional fatigue crack growth in simulated compressor blade by phase-field model","authors":"Shen Sun , Shijie Liu , Weiwei He , Xuan Zhang , Wei Tang , Liucheng Zhou , Min Yi","doi":"10.1016/j.ast.2025.110009","DOIUrl":"10.1016/j.ast.2025.110009","url":null,"abstract":"<div><div>High-cycle fatigue is a major concern for aeroengine compressor blades under complex cyclic mechanical and aerodynamic loads, but predicting fatigue behavior of blades remains challenging. Herein, a phase-field fatigue fracture model is applied to simulate the high-cycle fatigue behavior of the simulated compressor blade. In the phase-field model, a logarithmic degradation function is adopted to describe the fracture toughness decreasing with fatigue cycles. Cyclic loads are mimicked by the pressure applied on the blade surface. The three-dimensional (3D) fatigue crack propagation of the simulated blade is simulated. It is found that the fatigue crack initiates at the variable cross-section and propagates horizontally. Laser shock peening (LSP) is further shown to improve the fatigue properties, i.e., LSP induced compressive residual stress results in a 95% increase of fatigue life and notably retards the 3D fatigue crack growth. For the fatigue strength of both the original and LSPed blades, the predictions are within the <span><math><mo>±</mo><mn>5</mn><mtext>%</mtext></math></span> error band. The phase-field model here provides a predictive approach for the evaluation of high-cycle fatigue behavior and shows a great potential in the optimal design of durable and reliable compressor blades.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110009"},"PeriodicalIF":5.0,"publicationDate":"2025-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143349064","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Controlling the utility of wake capture in hovering flapping flight: An experimental investigation

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-03 DOI: 10.1016/j.ast.2025.110008

Hao Li , Samuel Weigert , Mostafa R.A. Nabawy

Flapping insect wings flip their direction of motion at stroke reversals, encountering the wake left behind from the previous half-stroke, which leads to changes in the instantaneous flow field and aerodynamic force production. This study identifies how to control the utility of this wing-wake interaction aerodynamic mechanism, also known as wake capture, by experimentally measuring the aerodynamic force coefficients of insect-like wings employing representative “normal hovering” kinematics. Dynamically similar model wings were driven by a custom-designed robotic manipulator to realise sinusoidal and semi-triangular flapping kinematic waveforms within a water tank. Forces were measured for wing planform shapes with different aspect ratio and radial area centroid location at a Reynolds number of 3000. Our experimental results show that for all wing planform shapes considered, a sinusoidal flapping waveform always leads to lower average wake capture lift and drag coefficients values than those produced from a semi-triangular flapping waveform. On the other hand, for the different wing planforms considered in this study, the wake capture force production increases with the increase of aspect ratio but decreases with the increase of radial centroid location.

{"title":"Controlling the utility of wake capture in hovering flapping flight: An experimental investigation","authors":"Hao Li , Samuel Weigert , Mostafa R.A. Nabawy","doi":"10.1016/j.ast.2025.110008","DOIUrl":"10.1016/j.ast.2025.110008","url":null,"abstract":"<div><div>Flapping insect wings flip their direction of motion at stroke reversals, encountering the wake left behind from the previous half-stroke, which leads to changes in the instantaneous flow field and aerodynamic force production. This study identifies how to control the utility of this wing-wake interaction aerodynamic mechanism, also known as wake capture, by experimentally measuring the aerodynamic force coefficients of insect-like wings employing representative “normal hovering” kinematics. Dynamically similar model wings were driven by a custom-designed robotic manipulator to realise sinusoidal and semi-triangular flapping kinematic waveforms within a water tank. Forces were measured for wing planform shapes with different aspect ratio and radial area centroid location at a Reynolds number of 3000. Our experimental results show that for all wing planform shapes considered, a sinusoidal flapping waveform always leads to lower average wake capture lift and drag coefficients values than those produced from a semi-triangular flapping waveform. On the other hand, for the different wing planforms considered in this study, the wake capture force production increases with the increase of aspect ratio but decreases with the increase of radial centroid location.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110008"},"PeriodicalIF":5.0,"publicationDate":"2025-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143304174","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A comprehensive study on dynamic responses of the whole aero-engine system and design of variable stiffness brackets

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-03 DOI: 10.1016/j.ast.2025.110010

Wentao Zhang , Kuan Lu , Yichi Zhang , Jin Chen , Dapeng Fu , Yang Yang , Chao Fu

The whole aero-engine usually consists of dual-rotor in the rotating parts and a stationary casing and accessory system. The study of the vibration characteristics and vibration reduction design of the aero-engine system has a critical impact on the performance of the aircraft. This paper delivers a comprehensive study of the dynamic response of the whole aero-engine system, which includes dual-rotor, casing, bracket, and accessories, taking into account the nonlinear bearings with Hertzian contact forces. To this end, the finite element (FEM) model of the entire aero-engine system is established. The sources of vibration and their transmission paths within the aero-engine were clearly identified via the analysis of amplitude-frequency curves, spectra and bifurcation diagrams. The optimal installation positions for the bracket and accessories were selected based on vibration energy analysis of the casing. A novel variable stiffness bracket, designed using the properties of shape memory alloys (SMA), was proposed for active vibration reduction of accessories. Experimental studies on stiffness regulation determined the overall stiffness of the bracket and its variation with temperature. Dynamic simulations confirmed that the bracket could effectively avoid the resonance frequencies of the accessories, resulting in a significant reduction in vibration amplitude. This research offers valuable engineering guidance for the design of aero-engine components and the vibration reduction and isolation of accessories.

{"title":"A comprehensive study on dynamic responses of the whole aero-engine system and design of variable stiffness brackets","authors":"Wentao Zhang , Kuan Lu , Yichi Zhang , Jin Chen , Dapeng Fu , Yang Yang , Chao Fu","doi":"10.1016/j.ast.2025.110010","DOIUrl":"10.1016/j.ast.2025.110010","url":null,"abstract":"<div><div>The whole aero-engine usually consists of dual-rotor in the rotating parts and a stationary casing and accessory system. The study of the vibration characteristics and vibration reduction design of the aero-engine system has a critical impact on the performance of the aircraft. This paper delivers a comprehensive study of the dynamic response of the whole aero-engine system, which includes dual-rotor, casing, bracket, and accessories, taking into account the nonlinear bearings with Hertzian contact forces. To this end, the finite element (FEM) model of the entire aero-engine system is established. The sources of vibration and their transmission paths within the aero-engine were clearly identified via the analysis of amplitude-frequency curves, spectra and bifurcation diagrams. The optimal installation positions for the bracket and accessories were selected based on vibration energy analysis of the casing. A novel variable stiffness bracket, designed using the properties of shape memory alloys (SMA), was proposed for active vibration reduction of accessories. Experimental studies on stiffness regulation determined the overall stiffness of the bracket and its variation with temperature. Dynamic simulations confirmed that the bracket could effectively avoid the resonance frequencies of the accessories, resulting in a significant reduction in vibration amplitude. This research offers valuable engineering guidance for the design of aero-engine components and the vibration reduction and isolation of accessories.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110010"},"PeriodicalIF":5.0,"publicationDate":"2025-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143304173","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

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